Nickel-base alloy
The alloy contains in wt.%: 13-15 of chromium, 2.8-3.5 of molybdenum, 1.4-1.9 of aluminum, 2.3-3.0 of titanium, 1.8-2.4 of niobium, 0.001-0.05 of boron, 0.001-0.005 of cerium, 0.001-0.01 of lanthanum, 0.001-0.1 of magnesium, no more than 0.08 of carbon, 0.5-2.0 of iron, the rest being nickel.
The invention will now be explained with reference to examples of specific embodiments thereof.
Table 1 __________________________________________________________________________ Heat resistance Mechanical properties 650.degree. 750.degree. Rela- rela- rela- Ulti- tive Impact sta- tive sta- tive mate Yield elon- viscos- bili- elon- bili- elon- strength limit gation ity stress ty, gation stress ty, gation kg/mm.sup.2 kg/mm.sup.2 % kg/mm.sup.2 kg/mm.sup.2 hrs % kg/mm.sup.2 hrs % __________________________________________________________________________ Alloy of the 120 75 16 5 72 100 6-8 40 100 8-10 invention 74 51 42 50 E1437BU 100 68 13 3 65 30 3-4 30 100 3-4 35 50 INKO 713C 88 76 8 2 70 100 2-3 56 100 1.5 __________________________________________________________________________
EXAMPLE 1The alloy had the following wt.% composition: 0.04 of carbon, 13 of chromium, 1.5 of aluminum, 2.4 of titanium, 2.8 of molybdenum, 1.9 of niobium, 0.001 of lanthanum, 0.001 of magnesium, 0.005 of cerium, 0.005 of boron and 1.0 of iron, the rest being nickel.
Said alloy was subjected to thermal treatment which consisted in elevated temperature hardening at a temperature of 1100.degree. C. during 8 hours with subsequent air cooling.
This was followed by air hardening, after the alloy had been aged at 1000.degree. C. during 4 hours. After that, the alloy was subjected to ageing at a temperature of 775.degree. C. during 16 hours, with subsequent air cooling, and then, to ageing at a temperature of 700.degree. C. during 16 hours, also with subsequent air cooling.
After said thermal treatment, the proposed alloy had the following properties:
ultimate strength, 120 kg/mm.sup.2 ;
yield limit, 75 kg/mm.sup.2 ;
relative elongation, 20%;
impact strength, 5 kg/mm.sup.2 ;
100-hour heat resistance at 750.degree. and under a stress of 40 kg/mm.sup.2, and at 650.degree., under a stress of 72 kg/mm.sup.2.
EXAMPLE 2The alloy had the following wt.% composition: 0.07 of carbon, 15 of chromium, 1.8 of aluminum, 2.6 of titanium, 2.2 of niobium, 3.2 of molybdenum, 0.01 of lanthanum, 0.005 of cerium, 0.005 of boron, the rest being nickel.
Said alloy was subjected to thermal treatment consisting in hardening at a temperature of 1100.degree. C. during 8 hours, with subsequent air cooling.
This was followed by air hardening, after the alloy had been aged at 1000.degree. C. during 4 hours.
After that, the alloy was subjected to ageing at a temperature of 775.degree. C. during 16 hours, with subsequent air cooling, and then, ageing at a temperature of 700.degree. C. during 16 hours, with subsequent air cooling.
After said thermal treatment, the proposed alloy had the following properties:
ultimate strength, 125-130 kg/mm.sup.2 ;
yield limit, 80 kg/mm.sup.2 ;
relative elongation, 16%;
impact strength, 4 kg/mm.sup.2 ;
100-hour heat resistance at 750.degree. C. and under a stress of 42 kg/mm.sup.2, and at 650.degree. C., under a stress of 74 kg/mm.sup.2.
The reasonably alloyed high-temperature nickel-base alloy of the proposed composition possesses high mechanical properties and high resistance; it also displays good workability which makes for its wide use for manufacturing turbine disks, power rings and other parts operating at temperatures of up to 750.degree. C. and under high rated stresses.
The rationally chosen ratio of the alloying elements in the novel alloy ensures a good combination of strength and plasticity characteristics which are of vital importance for a reliable prolonged operation of the most essential heavy-duty parts of jet engines.
Claims
1. A nickel-base alloy consisting essentially of in wt.%: 13-15 of chromium, 2.8-3.5 of molybdenum, 1.4-1.9 of aluminum, 2.3-3.0 of titanium. 1.8-2.4 niobium, 0.001-0.05 of boron, 0.001-0.005 of cerium, 0.001-0.01 of lanthanum, 0.001-0.1 of magnesium, no more than 0.08 of carbon, 0.5-2.0 of iron, the rest being nickel.
2. A nickel-base alloy according to claim 1 consisting essentially of in weight percent: 13 of chromium, 2.8 of molybdenum, 1.5 of aluminum, 2.4 of titanium, 1.9 of niobium, 0.005 of boron, 0.005 of cerium, 0.001 of lanthanum, 0.001 of magnesium, 0.04 of carbon, 1.0 of iron, the rest being nickel.
| 2104836 | January 1938 | Hessenbruch |
| 2570193 | October 1951 | Bieber et al. |
| 3744996 | July 1973 | Shaw et al. |
Type: Grant
Filed: Jun 14, 1977
Date of Patent: Dec 5, 1978
Inventors: Kuzma I. Terekhov (Moscow), Alexei T. Tumanov (Moscow), Alexandra P. Ozerova (Moscow), Valentin V. Topilin (Elektrostal), Mikhail Y. Dzugutov (Elektrostal), Mara A. Ljubinskaya (Elektrostal), Gennady A. Pashchnik (Elektrostal), Alexandr S. Nikishov (Moscow), Terenty I. Ustinov (Kuibyshev)
Primary Examiner: R. Dean
Law Firm: Haseltine, Lake & Waters
Application Number: 5/806,505
International Classification: C22C 1905;
